This paper reports on work completed to develop an analytical method for predicting the transient nonlinear response of a complete aircraft engine system due to the loss of a fan blade, and to validate the analysis by comparing the results against actual blade loss test data. The solution, which is based on the component element method, accounts for rotor-to-casing rubs, high damping, and rapid deceleration rates associated with the blade loss event. A comparison of test results and predicted response show good agreement except for an initial overshoot spike not observed in test. The method is effective for analysis of large systems.
Blade loss transient dynamic analysis of turbomachinery
Analyse des Schwingungsverhaltens von Flugzeugturbinen bei Schaufelverlust
AIAA Journal ; 21 , 8 ; 1134-1138
1983
5 Seiten, 13 Bilder, 1 Tabelle, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
Blade loss transient dynamic analysis of turbomachinery
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